Related Questions

The primary unbalanced force due to inertia of reciprocating parts in a reciprocating engine is given by (where m = Mass of reciprocating parts, $$\omega $$ = Angular speed of crank, r = Radius of crank, $$\theta $$ = Angle of inclination of crank with the line of stroke and n = Ratio of the length of connecting rod to radius of crank)
A $${\text{m}}{\omega ^2}{\text{r}}\sin \theta $$
B $${\text{m}}{\omega ^2}{\text{r}}\cos \theta $$
C $${\text{m}}{\omega ^2}{\text{r}}\frac{{\sin 2\theta }}{{\text{n}}}$$
D $${\text{m}}{\omega ^2}{\text{r}}\frac{{\cos2\theta }}{{\text{n}}}$$
The secondary unbalanced force due to inertia of reciprocating parts in a reciprocating engine is given by (where m = Mass of reciprocating parts, $$\omega $$ = Angular speed of crank, r = Radius of crank, $$\theta $$ = Angle of inclination of crank with the line of stroke and n = Ratio of the length of connecting rod to radius of crank)
A $${\text{m}}{\omega ^2}{\text{r}}\sin \theta $$
B $${\text{m}}{\omega ^2}{\text{r}}\cos \theta $$
C $${\text{m}}{\omega ^2}{\text{r}}\frac{{\sin 2\theta }}{{\text{n}}}$$
D $${\text{m}}{\omega ^2}{\text{r}}\frac{{\cos2\theta }}{{\text{n}}}$$
In turbo fan engine, the jet velocity as compared to turbojet engine is
A Less
B More
C Same
D May be less or more depending upon speed
The turbine of the turboprop engine is __________ that of the turbojet engine.
A Same as
B Smaller than
C Bigger than
D None of these
By fitting an air vessel to the reciprocating pump, there is always a saving of work done and subsequently saving of power. The saving in case of a double acting reciprocating pump is
A 39.2%
B 48.8%
C 84.8%
D 88.4%
By fitting an air vessel to the reciprocating pump, there is always a saving of work done and subsequently saving of power. This saving in case of a single acting reciprocating pump is
A 39.2%
B 48.8%
C 84.8%
D 88.4%
In a reciprocating engine, usually __________ of the reciprocating masses are balanced.
A One-half
B Two-third
C Three-fourth
D Whole
The maximum propulsive efficiency of a turbojet engine is at a speed of
A 1000 km/h
B 2000 km/h
C 2400 km/h
D 3000 km/h
A simple turbojet engine is basically
A A propeller system
B Gas turbine engine equipped with a propulsive nozzle and diffuse
C Chemical rocket engine
D Ramjet engine
The tractive force in a locomotive with two cylinders is given by (where c = Fraction of reciprocating parts per cylinder, m = Mass of reciprocating parts, $$\omega $$ = Angular speed of crank, r = Radius of crank and $$\theta $$ = Angle of inclination of crank to the line of stroke)
A $${\text{m}}{\omega ^2}{\text{r}}\cos \theta $$
B $${\text{cm}}{\omega ^2}{\text{r}}\sin \theta $$
C $$\left( {1 - {\text{c}}} \right){\text{m}}{\omega ^2}{\text{r}}\left( {\cos \theta - \sin \theta } \right)$$
D $${\text{m}}{\omega ^2}{\text{r}}\left( {\cos \theta - \sin \theta } \right)$$

Next steps